XFOIL Version 6.96 Calculated polar for: B-29 ROOT AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.2010 0.06783 0.06331 -0.0611 1.0000 0.0388 -19.500 -1.2027 0.06470 0.06012 -0.0621 1.0000 0.0393 -19.250 -1.2038 0.06169 0.05705 -0.0630 1.0000 0.0397 -19.000 -1.2030 0.05896 0.05426 -0.0638 1.0000 0.0402 -18.750 -1.2012 0.05633 0.05158 -0.0644 1.0000 0.0406 -18.500 -1.1994 0.05376 0.04895 -0.0650 1.0000 0.0410 -18.250 -1.1963 0.05136 0.04649 -0.0655 1.0000 0.0414 -18.000 -1.1917 0.04917 0.04424 -0.0659 1.0000 0.0418 -17.750 -1.1873 0.04697 0.04198 -0.0662 1.0000 0.0421 -17.500 -1.1853 0.04458 0.03954 -0.0664 1.0000 0.0425 -17.250 -1.1812 0.04245 0.03737 -0.0666 1.0000 0.0429 -17.000 -1.1762 0.04047 0.03534 -0.0666 1.0000 0.0435 -16.750 -1.1701 0.03862 0.03347 -0.0665 1.0000 0.0442 -16.500 -1.1592 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0.4300 0.6527 3.250 0.3881 0.00821 0.00265 0.0066 0.4274 0.6673 3.500 0.4092 0.00820 0.00270 0.0080 0.4243 0.6807 3.750 0.4301 0.00823 0.00276 0.0094 0.4210 0.6941 4.000 0.4491 0.00825 0.00282 0.0112 0.4173 0.7096 4.250 0.4665 0.00828 0.00290 0.0133 0.4137 0.7250 4.500 0.4853 0.00828 0.00296 0.0151 0.4115 0.7402 4.750 0.5030 0.00828 0.00301 0.0172 0.4091 0.7551 5.000 0.5189 0.00828 0.00308 0.0196 0.4063 0.7714 5.250 0.5348 0.00830 0.00317 0.0221 0.4032 0.7889 5.500 0.5506 0.00837 0.00329 0.0245 0.3999 0.8050 5.750 0.5656 0.00845 0.00343 0.0270 0.3964 0.8239 6.000 0.5846 0.00851 0.00357 0.0287 0.3939 0.8415 6.250 0.6063 0.00858 0.00371 0.0298 0.3915 0.8593 6.500 0.6295 0.00867 0.00386 0.0306 0.3887 0.8763 6.750 0.6567 0.00879 0.00405 0.0305 0.3854 0.8924 7.000 0.6859 0.00898 0.00427 0.0298 0.3807 0.9046 7.250 0.7157 0.00918 0.00448 0.0290 0.3754 0.9160 7.500 0.7523 0.00936 0.00469 0.0268 0.3700 0.9242 7.750 0.7814 0.00959 0.00492 0.0261 0.3645 0.9326 8.000 0.8217 0.00988 0.00520 0.0229 0.3562 0.9368 8.250 0.8524 0.01026 0.00553 0.0215 0.3444 0.9427 8.500 0.8766 0.01058 0.00584 0.0216 0.3338 0.9493 8.750 0.9089 0.01101 0.00624 0.0198 0.3238 0.9527 9.000 0.9361 0.01139 0.00661 0.0192 0.3156 0.9575 9.250 0.9525 0.01186 0.00706 0.0206 0.3081 0.9646 9.500 0.9814 0.01229 0.00749 0.0194 0.3004 0.9667 9.750 1.0046 0.01292 0.00808 0.0191 0.2897 0.9695 10.000 1.0252 0.01357 0.00870 0.0192 0.2797 0.9729 10.250 1.0365 0.01424 0.00936 0.0210 0.2708 0.9785 10.500 1.0587 0.01511 0.01019 0.0202 0.2587 0.9801 10.750 1.0773 0.01619 0.01120 0.0198 0.2432 0.9821 11.000 1.0920 0.01745 0.01239 0.0196 0.2260 0.9847 11.250 1.1028 0.01891 0.01378 0.0199 0.2082 0.9878 11.500 1.1060 0.02077 0.01555 0.0209 0.1886 0.9912 11.750 1.1140 0.02264 0.01736 0.0209 0.1726 0.9937 12.000 1.1259 0.02443 0.01910 0.0202 0.1596 0.9959 12.250 1.1394 0.02617 0.02081 0.0193 0.1489 0.9977 12.500 1.1507 0.02812 0.02273 0.0184 0.1379 0.9990 12.750 1.1622 0.03003 0.02462 0.0176 0.1292 0.9999 13.000 1.1585 0.03185 0.02642 0.0198 0.1221 1.0000 13.250 1.1538 0.03375 0.02830 0.0220 0.1139 1.0000 13.500 1.1522 0.03555 0.03011 0.0238 0.1100 1.0000 13.750 1.1489 0.03756 0.03212 0.0255 0.1030 1.0000 14.000 1.1469 0.03954 0.03409 0.0270 0.0974 1.0000 14.250 1.1416 0.04191 0.03645 0.0285 0.0909 1.0000 14.500 1.1422 0.04386 0.03841 0.0296 0.0868 1.0000 14.750 1.1394 0.04616 0.04070 0.0308 0.0818 1.0000 15.000 1.1395 0.04827 0.04283 0.0317 0.0782 1.0000 15.250 1.1382 0.05054 0.04510 0.0326 0.0744 1.0000 15.500 1.1401 0.05261 0.04721 0.0333 0.0723 1.0000 15.750 1.1421 0.05467 0.04928 0.0339 0.0696 1.0000 16.000 1.1423 0.05698 0.05162 0.0344 0.0679 1.0000 16.250 1.1450 0.05905 0.05371 0.0349 0.0659 1.0000 16.500 1.1462 0.06134 0.05603 0.0353 0.0639 1.0000 16.750 1.1483 0.06355 0.05827 0.0356 0.0624 1.0000 17.000 1.1485 0.06600 0.06075 0.0359 0.0607 1.0000 17.250 1.1516 0.06817 0.06296 0.0361 0.0595 1.0000 17.500 1.1553 0.07029 0.06510 0.0362 0.0583 1.0000 17.750 1.1560 0.07280 0.06765 0.0363 0.0569 1.0000 18.000 1.1581 0.07515 0.07003 0.0363 0.0556 1.0000 18.250 1.1579 0.07779 0.07270 0.0363 0.0542 1.0000 18.500 1.1609 0.08008 0.07504 0.0362 0.0535 1.0000 18.750 1.1645 0.08232 0.07730 0.0361 0.0523 1.0000 19.000 1.1650 0.08496 0.07999 0.0359 0.0512 1.0000 19.250 1.1663 0.08751 0.08256 0.0356 0.0500 1.0000